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首页> 外文期刊>International Journal of Turbomachinery, Propulsion and Power >The Influence of Combustor Swirl on Pressure Losses and the Propagation of Coolant Flows at the Large Scale Turbine Rig (LSTR): Experimental and Numerical Investigation
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The Influence of Combustor Swirl on Pressure Losses and the Propagation of Coolant Flows at the Large Scale Turbine Rig (LSTR): Experimental and Numerical Investigation

机译：大型涡轮机燃烧室涡流对压力损失和冷却剂流传播的影响：实验和数值研究

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摘要

The aerothermal interaction of the combustor exit flow on the first vane row has been examined at the Large Scale Turbine Rig (LSTR) at Technische Universit?t Darmstadt (Darmstadt, Germany). A baseline configuration of axial inflow and a variation of swirling combustor inflow have been studied. The nozzle guide vane (NGV) featured endwall cooling, airfoil film cooling and a trailing edge slot ejection as well as NGV-rotor wheel space purge flow. CO2 is injected for coolant flow tracing. The results are compared to five hole probe (5HP) measurements. The experiments for the baseline configuration are accompanied by numerical simulations using a passive scalar tracking method to validate the results and study the propagation of the coolant flow. The endwall coolant injection is detected to influence the pressure losses in the NGV. It has an impact on the Trailing Edge (TE) coolant ejection as well. For swirling combustor inflow, increased NGV pressure losses and increased mixing of Rear Inner Discharge Nozzle (RIDN) coolant and main flow is observed. An influence of the clocking position of the swirler to the vane is detected. Additional losses within the NGV row can be assigned to the swirler by means of flow tracing.
机译：达姆施塔特工业大学（德国达姆施塔特）的大型涡轮钻机（LSTR）已检查了第一排叶片上燃烧室出口流的热力相互作用。研究了轴向流量的基线配置和涡流燃烧室流量的变化。喷嘴导向叶片（NGV）具有端壁冷却，翼型薄膜冷却和后缘狭槽喷射以及NGV转子叶轮空间吹扫流的功能。注入CO2用于跟踪冷却液流。将结果与五孔探针（5HP）测量结果进行比较。对于基线配置的实验，使用无源标量跟踪方法进行数值模拟，以验证结果并研究冷却剂流的传播。检测到端壁冷却液喷射会影响NGV中的压力损失。它也对后缘（TE）冷却液喷射产生影响。对于涡旋式燃烧器流入，观察到NGV压力损失增加，并且后部内部排放喷嘴（RIDN）冷却剂和主流混合增加。检测到旋流器的计时位置对叶片的影响。 NGV行内的其他损耗可通过流跟踪分配给旋流器。

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